Flying machine having revolving supporting surfaces



Jan. 1, 1935. BREGUET ET AL 1,986,709

FLYING MACHINE HAVING REVOLVING SUPPORTING SURFACES Filed May 25, 1934 '8 Sheets-Sheet l 8 Sheets-Sheet 2 Jan. 1, 1935. L BREGUET ET AL FLYING MACHINE HAVING REVOLVING SUPPORTING SURFACES Filed May 25, 1954 Jan. 1, 1935. L. BREGUET ET AL 1,986,709

FLYING MACHINE HAVING REVOLVING SUPPORTING SURFACES I Filed May 23, 1934 8 Sheets-Sheet 3 I Jan. 1, 1935. BREGUET ET AL 1,986,709

FLYING. MACHINE HAVING REVOLVING SUPPORTING SURFACES Filed May 25, 1954 8 Sheets-Sheet 5 Jan. 1, 1935. L. BREGUET El AL FLYING MACHINE HAVING REVOLVING SUPPORTING SURFACES Filed May 23, 1934 8 Sheets-Sheet 6 Jan. 1, 1935. L BREGUU ET AL 1,986,709

FLYING MACHINE HAVING REVOLVING SUPPORTING SURFACES Filed May 23, 1934 a Shets-Sheet "I Jan. 1, 1935, BREGUET ET AL V ,28

V FLYING MACHINE HAVING REVOLVING SUPPORTING-SURFACES Filed May 23, 1934 8 Sheets-Sheet 8 Patented Jan. 1, 1935 FLYING MACHINE HAVING REVOLVING SUPPORTING SURFACES Louis Breguet and Rene Dorand, Paris, France;

said Dorand aaaignor to said Bregnet Application May 23, 1934, Serial No. 727,184 In France May 27, 1938 r1 Claims. (01. zu-io) The present invention relates to gyroplanes, or flying machines having revolving supporting sur-'-- faces, of the type described in our U. 8. Patent No. 1,919,089,1i1ed May'14, 1931.

The general object of the present invention is to provide improvements to flying machines of this type. 4 a

It is of primary importance that, in case of stopping of the engine, the helicopter should automatically switch to gliding flight without it being necessary to adjust the angle of incidence of the blades or 'airfoils. Furthermore this gliding flight should advantageously be obtained with a, minimum vertical speed. 4

If, at the time-when the engine stops, the pitch of the airfoils is such that the mean angle of attack of the blade is equal to, or greater than, an angle approximating the incidence for which the ratio of lift and drag is maximum, the wings or blades of an ordinary helicopter stop turning and autorotation is not maintained in the normal direction of revolution. g

If the device is provided with automatic incidence adjusting means such as those indicatedin the U. S patent above referred to, the set of wings or blades, under the same conditions of incidence when flying with the engine running, keeps turning, in case of stopping of theengine,

. by autorotatlon, in the proper direction.

the incidence of the setof wings is too great when flying with the engine runningat a given speed (case of a machine in which the load per square meter is very high) and if the engine stops, autorotation is maintained. But it does not take place under thebest possible conditions.

A flrst improvement according to the present invention consists in automatically obtaining a reduction of the pitch when the engine stops by making use not only of the upward relative displacement of the blade or wing, that is to say its rotation about the horizontal axis of the Cardan joint through which said blade or wingjsconnected to the vertical shaft,

but alsff'thb relative forward movement of the.

wing or blade ceases to-be pushed in a backward direction by the aerodynamic resistances and is urged forward by the centrifugal forces (Figs. 1 and 2).

Another improvement according to the present invention consists in. an embodiment of the auto- .matic adjusting device in' which the arm extending ahead of each blade and bearing through its free endupon a roller path is replaced by a toothed sector flxed to the blade and gearing 'with a bevel pinion flxed to one end of the vertical or horizontal spindle of the Cardan joint, the pinion meshing in'tum with it may be either flxed to the hub or actuated through a suitable connected to the hub of the set of wings through an arm provided at each end with a Cardan join and supporting a tail part.

.about a longitudinal member and the latter is According to the presentinvention, the automatic adjusting device includes a system of connecting rods and levers articulated to one another through Cardan joints orball and socket joints, this system serving to connect the end of a piece driven by the hub of the set of wings with the front edge of the blade or wing, one of the connecting rods extending longitudinally through the front portion of the tail part of the arm.

According to another embodiment, adapted to be used in'the case in whichthe incidence of the blade is controlled indirectly through servo-motors, for instance movable shutters or ailerons, the system of rods and levers connects the piece driven by said hub with said servo-motor.-

Other features of the presentinvention will appear from the following detailed description thereof.

Preferred embodiments of the present invention, will be hereinafter described with reference to the accompanying drawings, given merely by way of example, and in which:

Figs. 1 and 2 are diagrammatic plan views showing the angular displacements of the blades of wings ina forward direction when the engine stops;

Fig. 3 is a perspective view of a portion of an improved gyroplane according to the present invention;

Fig. 4 is a diagrammatic detail view corresponding to Fig. 3;

Fig. 5 is a diagrammatical view illustrating the working of the device of Fig. 3;

Figs. 6, 7, 8 and 9 show different embodiments of the automatic adjusting device including a system of gears;

Fig. 10 is a perspective view showing the opposed blades of a helicopter provided with the automatic adjusting device diagrammatically shown in Fig. 6;

Fig. 11 is a perspective view showing two opposed blades of a helicopter provided with an automatic adjusting device according to the embodiment illustrated by Fig. 8;

Fig. 12 shows, on a larger scale, a modification of the device of Fig. 11, in which the reduction of the pitch is obtained automatically with the insertion of a reducing gear when the blades of the helicopter work with autorotation;

Fig. 13 shows a helicopter having two super posed sets of wings or blades mounted in such manner that when the sets of wings start into autorotation (stoppage of the engine) the lower set of wings driven by the relative wind has a driving action, while the upper set of wings is in turn driven by the lower set of wings;

Fig. 14 shows the automatic adjusting device applied to a set of wings each of which is made of two portions jointed together, the -bladei'being shown with a great incidence;

Fig. 15 shows the same device which the incidence of the blade is smaller}; Y

Fig. 16 is a modification of the automatic ade justing device just above referred to, intende d' to {I be used in connection with wings provided-with movable shutters, the shutter being s l iownjjin "a position corresponding-tea small-incidence;

of the shutter being'greateL- Fig. 17 is a view similar to Fig. 1'6,th e-incidence- When the machine iszin-fligh t and theengine stops, the driving; torque; whichact'sin the dia rection of arrows'f,,f," Fig.- l, becomes zero and the blades 11, jointedthroughf-ca'rdanfjoints 51 to the ends of arm 6,:'which;. -is:keyed on the vertical shaft 2, cease to be pulled in a'backward direction by the aerodynamic resistances and are urged forwardly by the centrifugal forces. These blades therefore come into the position shown by Fig. 2, turning through a relative angle or. This relative angular, displacement in a forward direction, that is to say in the direction of revolution of the blades, will be utilized, according to the present invention, for obtaining an automatic reduction of the pitch of the sets of blades or wings.

This result can be obtained through the device illustrated by Fig. 3.

The general arrangement of this device was described in the first patent of addition, No. 42,792, of May 28, 1932, relating to French Patent No. 711,456 (which corresponds to our U. S. Patent No. 1,919,089, above referred to). As shown in Fig. 3, the arm 3 of each blade 1 carries a lever 3a connected to the arm 48 of the rotary drum or plate 47 through a rod 7, provided with a Cardan joint at 7a and with a ball and socket joint at 71). The arm 3 of wing 1 is articulated on the vertical driving shaft of the gyroplane horizontally about 5151 and vertically about 52-52.

Drum 47 is rigid with the outer ball cage of ball bearing, also action as a-ball thrust bearing, 45. The inner ball cage 9 (Fig. 4) of this ball bearing is connected through gimbal joint in-,

, Z Z to support 46a and controlled or links F, F.

ment is produced by acting on a bar E fixed to support 46a and which is the general control blades 1, turning in the direction-of arrow f,v

through connecting rods M M jointed together about a horizontal axis Y, Y and jointed respectively to hub 40 and to drum 47 about a horizontal axis X X and through a ball and socket joint Q respectively.

Under these conditions, drum 47 can rotate in aplane inclined with respect to a plane at right angles to the main axis of revolution of the set of .wings.

The inclination of drum 47 is obtained by acting on the inner ball cage 9, which does not rotate, of the ball bearing of said drum, by means of connecting rods 11, 11 jointed with said ball cage through a Cardan joint 12. These connecting rods are jointed through ball and socket joints 13, 13' at their lower ends with bent levers L, L, themselves pivoted about horizontal axes through rods These bent levers make it possible to compensate .for the difference of phase existing between the instinctive action exerted by the pilot on the control organ, such as F, and the displacement of the flying machine in response to the action of the pilot. If, for instance, the pilot wishes to lift the front of the machine (assuming the front of the machine to be on the left hand side of the drawings, the plane of which is supposed to be .the plane of symmetry of the machine), he will instinctively push upwardly lever F, located opposite him. The joint 13' of connecting rod 11 is located in front of the plane of the drawings,

with an angle 0:, so that the top of .the curve described by point 7b (lower end of the connecting rod 7 for varying the incidence of blade 1) will be positioned in front of the plane of the drawings. But as the front end7a of connecting rod 7 and of rod 3a is itself positioned in front of the plane of symmetry, with an angle 13 substantially equal to a, the wing will consequently be given its maximum incidence when passing in the vicinity of the plane of symmetry. 7

According to the present invention, arm 7, which in the prior arrangement disclosed by Fig. 1 of the French patent of addition No. 42,792, above referred to, was disposed substantially at right angles to arm 3a, now makes with said arm So, as shown by Fig. 3, an angle 'y smaller than 90.

Under these conditions, any relative angular displacement of the blade in a forward direction, that is to say in the direction of rotation, produces a reduction of the pitch, as shown by the diagrammatic view of Fig. 5. It is clearthat when rod 7, which pivots about its lower end 7b, passes from the position shown in solid lines to the position shown in dotted lines 7', which corresponds to a forward relative angular displacement of the blade, said blade also turns about its longitudinal axis, in such manner as to reduce the angle of incidence.

In order to obtain the automatic incidence adjusting means, we may, s shown in Figs. 6 to 11 inclusive, provide, instead of an arm 3a extendabsence ing in a i'orward direction, a toothed sector 3'!) tired to the hub 3 oi! blade 1 and meshing with a pinionfl' mounted loose at the end 01 the horiaontal spindle 52' oi the Cardan joint a or the blade, the angular position of this pinion 7' being used by another toothed sector b which may be rigidwithhubeo.

when blade 1 moves with a rela'tive forward movement with respect to the hub, by pivoting in the direction of arrow I about the vertical spindle iii of the Cardan joint, pinion 7' remaining stationary, toothed sector 3'b rolling along with-the massa es-o th posed-blades -1 ma vertical axis-51 '01 the Cardan joint piano- .turning about aneccentric. part. c

the teeth or this pinion, causes the blade to turn in a downward direction, that is to say in the direction that reduces the angle of incidence. This reduction of the incidence also takes place automatically when the blade turns upwardly when the engine stops. V b

This mechanism including a toothed sector and a pinion can be made in any suitable manner, for instance asshown in Figs. 8, '1, 8 and 9. In these the same. or corresponding, organs aredesignatedby the same reference characters In the embodiment of Fig. 10, sector b,-in stea or being fixed to hub 40, is pivoted'about-zth subjecte'd'to' the actionotcontrol means apa'bl'e oi-"giving said sector an alternatinglgoscillatory movement of small amplitude, which improve the propulsion (as indicated in the U S. pht iit' above referred to) the pitch of the blade decrees- 1 1,18 when said blade..move sagainst-thievgin whi e it increases when;' the blade-is the same direction as. thewindi,

may for" instance" co connecting-mod 7c articulatedfiat' itsl .enids nesting-rode carrieswo In the embodiment shown-i11 matic incidence regulating mfec toothed sectors and pinion meshingjtherewith similar to that shown by 8;fbii the. en of sections b are further connected to-rodsiM', these prolonged ends b playing the same, part as the connecting rods M o! the device shown in Fig. 3. As shown by,Flg. 1l, it is now the whole of the prolonged part b and of the connecting rod W that ensures the connection between rod 40 .and ring 47. The mechanism is operated as explained in the U. S. patent above referred to and in the part of the preceding description that relates to Fig. 3. As a matter of fact, Fig. 11 discloses the' rod E that serves to control the variations of the pitch of the set of wings by vertical displacement or ring 46a, while rods F (acting through the Cardan joints we on ring 9a) and rod h" (acting through connecting rod 11a on said ring 94) make it possible to incline the apparatus in the desired direction and in two planes at right anglesto each other. In this Fig. 11, the rings of gimbal joint 8;! (jointed throl lgh 120 with rod F) and N (jointed through a pin 11? with rod F" and with rod lla. itselipivotally connected with ring 911) havebeen shown as being not concentric with each" other, this arrangement making it possible to reduce the space occupiedby the rotating parts, and also the diameter otthe bearings.

In the various embodiments abo'ye described, the incidence of the blade decreases by an angle equal to the angular displacement corresponding to an upward pivoting movement of the blade or to a forward angular displacement thereot with respect to'the hub. v

Fig. 11 shows a modification including multiplying gears which increase the automatic incidence adjusting action, which means that the angle by which the incidence is reduced is greater than the angle of displacement of the blade with respect to the hub. This case would app more especially to heavy sets 01' blades or to propellers. For this purpose, the pinion 7', which meshes with sector b, carries an arm h provided with a toothed sector i concentric with pinion 7' but having a greater radius. This sector i in turn meshes with a toothed sector 3'0 keyed on blade 1, the multi-' plicatlon resulting from the ratio oi the radiuses of sector i and pinion 7..

In the various examples that have just been described, we have considered only the case of a single set-of wings or blades. When the helicopter comprises two sets of wings or blades connected together through gear wheels, the effects of the adjustment of incidence, at the time when autorotation takes place, can be obtained by applying the improved-devices'according to the present invention to the motive set of wings, that is to say to the set oi. wheels that maintains the other set of heels in rotation during gliding flight, as shown y way of example in Fig. 13.

V In this embodiment, the lower set or wheels is .rovided with an automatic incidence regulating devi iii{including arms 3. and connecting rods 7 jointed with ring 47, the means for controlling the operating wheel 9', which makes it possible to anually. adjust the pitch of the lower set of wings 11' .f;-A S ":f i)l'i theupper set of wings '1", which .might havefa-nxed pitch, it is shown as provided withan' incidence adjusting device consisting of v m n-31.. the end of which is jointed with a conecting rod 7b itself pivoted about a vertical pivot .01 hub 40.; With such an arrangement it sutces" to -reduce the pitch of one of the sets of wingsor blades,- which in the case illustrated by Fig. 13 is the lower set of wings and the latter then drives hub 40 through shaft 0, bevel gear wheel a, shaft p and the reducing gear q In order to compensate ,Iorthe reaction exerted on the irame by the gears (due to the fact that the lower set of wings has a motive action when the engine is stopped; while the upper set of wings is actuated by this motive action) it sumces to turn the tail 1'. A free wheel t is advantageously interposed between the engine and the power attenbeingshown as consisting of a rack n and.

transmission system 9, q, r, in order that the rotation of the'sets of wings should notbe braked by the engine.

\ Fig. 14 clearly shows how the automatic incidence adjusting device can be utilized in the case of a blade 1 which is arranged to turn around itsarticulation (not necessary) about an axis 52 -52 at right angles to the first one. It a is the angle between the axis 31-31 of arm 3 and a plane at right angles to the axis of revolution and if 0 is the angle existing between the axis 60,-601 of the longitudinal. element 60 of the blade 1 and the plane defined by axis H1 I-I'r the present invention consists essentially in causing the pitch oi the blade to dependon these and axis 3z-3z, the improvement according to angles a and 0, by means of a mechanical device of any kind whatever arranged in such manner that any independent or simultaneous increase or decrease of these angles or of their sum involves an increase of the pitch angle shown at I.

Figs. 14 and 15 further show by way of example an embodiment of the automatic incidence adjusting device including connecting rods or links and the position-that it occupies for two different incidences of the blade.

The hub 40 drives a piece 48 which turns together with it and which might be actuated by the pilot, as stated in the U. S. patent above referred to.

The end 48y of piece 48 is pivotally connected through a ball and socket joint with the end of a connecting rod 61, which controls, through another ball and socket joint 62, a lever 63; The last mentioned lever is rigidly connected with a tube 64 pivoting about its axis and which displaces, through lever 65, connecting rod 67 and the ball and socket joint 68 which constitutes the connection with blade 1.

The working of this arrangement is the following: 4

When the angle or varies, increases for instance, the end 48 and piece 48 remains stationary, lever 63 is pivoted in a downward direction and causes tube 64 to pivot, this movement being transmitted to lever 65. The latter.

causes blade 1 to pivot about its axis 601-602 so that the incidence I decreases.

It will be readily understood that if a and 0 decrease or increase, I increases or decreases.

The angle 0 is therefore called upon, due to the combination of the levers, to play the same incidence regulating function as angle 0'. of the U. S. patent above referred to.

For instance, if, due to a whirlwind increasing the sustentation, blade 1 tends to move upwardly with respect to arm 3, the increase of angle 0 that results therefrom involves a suitable decrease of the pitch through the action of the cinematic device itself. The movement of the free blades is therefore guided in the case of strong whirlwinds and the blades do not undergo considerable oscillations which would be dangerous.

According to another embodiment, the incidence regulating device can be made by means of gear wheels and sectors as above described with reference to Figs. 6 to 12 when it is desired to vary I as a function of only angle :1.

Figs. 16 and 1'7 show, in two different positions another embodiment of the regulating device according to the present invention, in which the incidence can be controlled indirectly through a shutter 70, jointed at 71 to blade 1, parts 61, 62', 63', 64', 65', 66', 67' and 68 playing the same part as the corresponding parts 61, 62, 63, 64, 65, 66, 67, and 68 respectively of Figs. 14 and 15.

The servo-motor shutter 70, which might be disposed in front of the blade is shown, merely by way of example, under the trailing edge.

It will be readily understood that if the incidence s of the shutter increases, the simultaneous increase of the lift and of the drag that results therefrom creates a torque, which tends to reduce the angle of incidence of the blade.

While we have, in the preceding description, disclosed what we deem to be practical and eflicient embodiments of our invention, it should be well understod that we do not wish to be limited thereto as there might be changes made in the arrangement, disposition and form of the parts without departing from the principle of the invention as comprehended within the scope of the appended claims.

What we claim is:

1. A flying machine of the type described, which comprises in combination, an upright shaft, at least two blades or wings radially disposed on either side of said shaft, an arm for supporting each of said blades substantially parallel to the leading edge thereof, a universal joint and a. bearing for connecting said arm to said shaft, whereby said arm can rotate in any direction whatever with respect to said shaft and can revolve about its own longitudinal axis, means for controlling during the flight the angular position of said arm about its own longitudinal axis, and means for reducing the angle of incidence of said blade operative by a relative forward angular displacement of the blade with respect tosaid shaft.

2. A flying machine of the type described, which comprises in combination, an upright shaft, at least two blades or wings radially disposed on either side of said shaft, an arm for supporting each of said blades substantially parallel to the leading edge thereof, a universal joint and a bearing for connecting said arm to said shaft, whereby said arm can rotate in any direction whatever with respect to said shaft and can revolve about its own longitudinal axis, a guiding member slidably and pivotally mounted on said shaft, means for causing said member to slide along said shaft, means for causing said member to oscillate about any axis passing through said shaft and two levers jointed together and one of which is angularly connected with said arm and extends ahead of it in the direction of revolution of the shaft, while the other lever is operatively connected with said guiding member, the angle made by said levers with each other being smaller than 90", whereby a relative forward angular displacement of said blade with respect to said shaft causes the angle of incidence of the blade to be reduced through said levers.

3. Aflying machine of the type described, which comprises in combination, a revolving hub, a shaft for said hub, at least two blades or wings radially disposed on either side of said hub, an arm for supporting each of said blades substantially parallel to the leading edge thereof, a universal joint and a bearing for connecting said arm to said hub, whereby said arm can rotate in any direction whatever with respect to said hub and can turn about its own longitudinal axis, means for controlling during the flight the angular position of said arm about its 'own longitudi-. nal axis, a spindle carried by said universal joint passing through the center thereof, a pinion mounted loose on said spindle, a toothed member operatively connected with said hub and meshing with said pinion, and a toothed member operatively connected with said arm and meshing with said pinion, so that a relative forward angulardisplacement of said blade with respect to said shaft causes the angle of incidence of the blade to be reduced.

4. A flying machine of the type described, which comprises in combination, a revolving hub, a shaft for said hub, at least two wings or blades radially disposed on either side of said hub, an arm for supporting each of said blades substantialLv parallel to the leading edge thereof, a universal joint and a bearing for connecting said arm with said hub, whereby said arm can rotate in any direction whatever with respect to said,

hub and can turn about its own longitudinal axis, means for controlling during the flight the angular position of said arm about its own longitudinal axis, a spindle carried by said universal joint passing through the center thereof, a pinion mounted loose on said spindle, a toothed sector rigid with said hub and meshing with said pinion, and a toothed sector rigid with said arm and meshing with said pinion, so that a relative forward angular displacement of said blade with respect to said shaft causes the angle of incidence of the blade to be reduced.

5. A flying machine of the type described, which comprises in combination, a revolving hub, a shaft for said hub, at least two wings or blades radially disposed on either side of said hub, an arm for supporting each of said blades substantially parallel to the leading edge thereof, a universal joint and a bearing for connecting said arm with said hub, whereby said arm can rotate in any direction whatever with respect to said hub and can tumabout its own'longitudinal axis, means for controlling during the flight in the angular position of said arm about its own longitudinal axis, a spindle carried by said universal joint passing through the center thereof, a pinion. mounted loose on said spindle, a toothed sector pivoted to said hub, means operative by said shaft for imparting an oscillating movement of small amplitude to said toothed sector, said toothed sector being in mesh with said pinion and a toothed sector rigid with said arm and meshing with said pinion, said toothed sectors and said pinion being so disposed that a relative forward angular displacement of said blade with respect to said shaft causes the angle of incidence of the blade to be reduced.

6. A flying machine of the type described, which comprises in combination, arevolving hub, a shaft for said hub, at least two wings or blades radially disposed on either side of said hub, an arm for supporting each of said blades substantially parallel to the leading edge thereof, a universal joint and a bearing for connecting said arm with said hub, whereby said arm can rotate in any direction whatever with respect to said hub and can turn about its own longitudinal axis, means for controlling during the flight the angular position of said arm about its own longitudinal axis, a spindle carried by said universal joint passing through the center thereof, a pinion mounted loose on said spindle, a toothed sector operatively connected with said hub and meshing with said pinion, a toothed sector rigid with said arm and means for operatively connecting said last mentioned sector with said pinion so that the angle through which said last mentioned sector is caused to turn is greater than the angle through which said pinion turns, said toothed sectors and said pinions being so disposed that a relative forward angular displacement of said blade with respect to said shaft causes the angle of incidence of the blade to be reduced.

7. A flying machine according to claim 1 further comprising a secondpair of blades or wings mounted in the same manner about the axis of said shaft, and means, for transmitting the movement of the first pair of blades to the second pair of blades .when said first pair of blades is turning freely about said shaft.

comprises in combination, a revolving hub, at

least two blades or wings radially disposed on either side of said hub, each blade being made of two parts, an intermediate part and an end part, an arm supporting each intermediate part substantially parallel to the leading edge thereof, at least one swivel Joint, the axisof which is at right angles to the axis of said hub, for connecting said arm with said hub, a longitudinal member pivotally supporting the end part of said blade about an axis substantially parallel to the leading edge of said end part, at least one swivel joint, the axis of which is substantially parallel to the general plane of said intermediate part of the blade, for connecting said longitudinal memher to said arm, and means, operative by the rotary displacements of said parts of the blade about the axes of said Joints respectively, for controlling the incidence of said end part of the blade about the axis of said longitudinal member.

9. A flying machine of the type described, which comprises in combination, a revolvinghub, at least two blades or wings radially disposed on either side of said hub, each blade being made of two parts, an intermediate part and an end part, an arm for supporting each intermediate part substantially parallel to the leading edge thereof, at least one swivel joint, the axis of which is at right angles to the axis of said hub, for connecting said arm with said hub, a longitudinal member pivotally supporting the end part of said blade about an axis substantially parallel to the leading edge of said end part. at least one swivel joint, the axis of which is substantially parallel to the general plane of said intermediate part of the blade, for connecting said longitudinal member to said arm, and a system of articulated links interposed between said hub and said end part of the blade for controlling the incidence of said end part of the blade about the axis of said longitudinal member in accordance with the relative angular positions of said intermediate part and said end part with respect to said hub and said intermediate part respectively.

10. A flying machine of the type described, which comprises in combination, a revolving hub,

at least two blades or wings radially disposed on' either side of said hub, each blade being made of two parts, an intermediate part and an end part, an armfor supporting each intermediate part substantially parallel to the leading edge thereof, at least one swivel joint, the axis of which is at right angles to the axis of said hub, for connecting said arm with said hub, a longitudinal memberpivotally supporting the end part of said blade about an axis substantially parallel to the leading edge of said end'part, at least one swivel Joint, the axis of which is substantially parallel to the general plane of said intermediate part. for connecting said longitudinal member to said arm, a servo-motor for varying the incidence of said end part of the blade. and means interposed between said hub and said servo-motor and operative by rotary displacements of said parts of the blade about the axes of said joints respectively, for operating said servo-motor.

11. A flying machine according to claim 10 in which said servo-motor consists of an airfoil connected with said end part of the blade.

LOUIS BREGUET. RENE DORAND. 

